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Preparation method of variable-rigidity wear-resistant vibration-damping composite material

A composite material and stiffness technology, which is used in the preparation of variable stiffness wear-resistant and vibration-damping composite materials, can solve the problems of cracking damage, peeling resistance, falling application, poor coating elongation, etc., so as to reduce the wear and tear of composite materials. Interlayer delamination failure behavior, easy operation, and the effect of improving the overall service life

Pending Publication Date: 2022-01-28
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the poor elongation of the coating under the condition of large deformation and deflection, local cracks and damage, and the decline of the anti-stripping ability of the coating under the action of beating also seriously restrict its application on moving parts.

Method used

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  • Preparation method of variable-rigidity wear-resistant vibration-damping composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] A variable stiffness wear-resistant and vibration-damping composite material is prepared, the length is 100mm±5mm, the width is 80mm±5mm, and the thickness is 2.4mm±0.2mm. The total number of layers is 3, and the steps are as follows:

[0033] (1) The composite material substrate with a thickness of 1.6mm ± 0.2mm was prepared by the T700 carbon fiber / epoxy plain fabric prepreg autoclave process.

[0034] (2) The composite material substrate is coated with 3340 type adhesive after surface treatment and cleaning.

[0035] (3) On the surface of one side of the substrate coated with the 3340 type adhesive composite material, along the movable friction side to the other side, the hydrogenated nitrile unvulcanized rubber with a thickness of 0.2mm ± 0.05mm is pasted, and its length, width and compound The material base is the same.

[0036](4) Continuously cover 0.3mm±0.1mm thick reinforced wear-resistant fabric from the surface width of 10mm on one side of the composite mat...

Embodiment 2

[0040] A variable stiffness wear-resistant and vibration-damping composite material is prepared, with a length of 500mm±5mm, a width of 120mm±5mm, and a thickness of 3mm±0.2mm. The total number of layers is 5, and the steps are as follows:

[0041] (1) A composite material substrate with a thickness of 2mm±0.2mm was prepared by a glass fiber / phenolic resin twill prepreg molding process.

[0042] (2) The composite material substrate is coated with 34T adhesive after surface treatment and cleaning.

[0043] (3) A silicone rubber unvulcanized rubber with a thickness of 0.2mm ± 0.05mm is pasted on the surface of one side of the substrate coated with the 34T type adhesive composite material along the movable friction side to the other side surface, and its length, width and composite material are The base material is the same.

[0044] (4) Continuously cover 0.2mm±0.1mm thick nylon 66 reinforced wear-resistant fabric from the surface width of 20mm on one side of the composite mat...

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Abstract

The invention belongs to the technical field of composite materials, and relates to a preparation method of a variable-rigidity wear-resistant vibration-damping composite material. The composite material is prepared from a composite material base material, an adhesive, an unvulcanized rubber sheet and a reinforced wear-resistant fabric through composite mold pressing. Before forming, the composite material base material, the adhesive, the unvulcanized rubber sheet and the reinforced wear-resistant fabric are arranged in a gradient mode to form a blank, and then mold pressing vulcanization forming is conducted. The forming method is simple and convenient to operate, and the obtained product has the advantages of variable rigidity, wear resistance, vibration reduction and the like, can be used for sealing gaps among movable airfoils such as a main wing, an aileron, a flap and the like of an aircraft wing, can meet the maneuvering characteristics of an aircraft, and can improve the long-term service requirement of a composite material part.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and relates to a preparation method of a variable-rigidity wear-resistant and vibration-damping composite material. Background technique [0002] Resin-based composite materials have been widely used in the aerospace field due to their high strength ratio modulus, good structural design, and easy integration of structure and function. Traditional composite materials are often used for fixed parts, and their static load is considered in structural design. With the increasing application of composite materials, in active parts, such as the sealing structure between the flaperon and the fixed airfoil, higher requirements are put forward for the structural design, wear resistance, anti-beating and vibration reduction performance of composite materials. . [0003] In the cantilever beam sealing structure with one end fixed, the aerodynamic load acts on the surface of the sealing composit...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/34
CPCB29C70/345
Inventor 马绪强钱黄海王永梅董慧民李跃腾张艳军
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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